Ground Safety

Transcription

Ground Safety

Aircraft Recovery
Manual
Note: For the list of A/C effectivity supported by this manual, refer to the Aircraft
Maintenance Manual (AMM).
Publication No. BD-700 ARM
GLOBAL SERIES
AIRCRAFT RECOVERY MANUAL
Bombardier Aerospace
P. O. Box 6087, Station Centre-ville
Montreal, Quebec, Canada H3C 3G9
http://www.cic.bombardier.com
For more information regarding Technical Publication please contact:
Bombardier Customer Services Business Aircraft
Customer Response Center (CRC)
North America:
Outside North America:
Fax:
Email:
1-866-JET-1247 (1-866-538-1247)
1-514-855-2999
1-514-855-2535
[email protected]
Distribution & Ordering
Fax:
Email:
1-514-855-2770
[email protected]
To ease the ordering process, the following Document
Identification Number should be used: GL 700 ARM
It is understood that this documentation, comprising technical data and other information in any media
shall not be reproduced or disclosed in whole or in part without Bombardier's written authorization, is
proprietary and confidential to Bombardier and that all rights to patent, copyright, trademark, trade
secret and other intellectual property rights therein belong to Bombardier. Such documentation,
technical data and other information shall not be modified, translated, reverse assembled, reverse
engineered or de-compiled and shall be used solely to maintain, operate or repair the aircraft.
Copyright © 1998-2013 by Bombardier Inc. All rights reserved.
*Trademark of Bombardier Inc. or its subsidiaries.
Printed in Canada
BD−700 AIRCRAFT RECOVERY MANUAL
REVISION 12 − TRANSMITTAL LETTER
This package contains BD−700 AIRCRAFT RECOVERY MANUAL, Revision 12, dated Aug
06/2015.
Record the incorporation of Revision 12 on the RECORD OF REVISIONS sheet at the front of
your manual.
To bring your manual up to date, remove the old pages indicated below and insert the
corresponding new pages, according to the following list.
REMOVE:
Ch−Se−Su
Effective Pages
Section 02
INSERT:
Effectivity
Page
1−2
7−10, 13
Ch−Se−Su
Effectivity
Effective Pages
Section 02
Page
1−2
7−10, 13
EFFECTIVITY: ALL
TRANSMITTAL
Page 1
Aug 06/2015
USER COMMENTS
ON ERRORS, OMISSIONS, PROCEDURES (IF APPLICABLE), ETC.
To: Bombardier Business Aircraft, Customer Support
Department 631 (Technical Publications and Information)
From:
Date:
Address:
E−mail:
Aircraft S/N:
Telephone No.
(please print)
The following publication requires correction or clarification:
Publication:
Chap./Sect. No.
Page Date:
Page No.
Para No.
Comments:
You can send your user comment as follows:
− by telephone at (514) 855−9304
− by e−mail to [email protected]
− by fax at (514) 855−7894
− by mailing it to the address on the back of this page.
Fig. No.
Bombardier Business Aircraft, Customer Support
P.O. Box 6087, Station Centre−ville
Montreal, Quebec, Canada H3C 3G9
Attn:
User Comments Coordinator
Department 631
RECORD OF REVISIONS
A signature in the "INSERTED BY" column shows that
the publication holder has incorporated the revision.
REVISION NO.
ISSUE DATE
DATE INSERTED
INSERTED BY
1
Mar 31/1998
Mar 31/1998
Bombardier
2
Apr 30/1999
Apr 30/1999
Bombardier
3
Mar 22/2004
Mar 22/2004
Bombardier
4
Apr 26/2005
Apr 26/2005
Bombardier
5
Aug 02/2005
Aug 02/2005
Bombardier
6
Mar 28/2006
Mar 28/2006
Bombardier
7
Sep 15/2008
Sep 15/2008
Bombardier
8
Nov 07/2008
Nov 07/2008
Bombardier
9
Dec 22/2009
Dec 22/2009
Bombardier
10
Nov 30/2011
Nov 30/2011
Bombardier
11
Nov 22/2012
Nov 22/2012
Bombardier
12
Aug 06/2015
Aug 06/2015
Bombardier
RECORD OF TEMPORARY REVISIONS
TEMPORARY SECTION AND PAGE
REV. NO.
NO.
ISSUE
DATE
DATE
INSERTED
DATE
REMOVED
INSERTED
BY
REMOVED
BY
LIST OF EFFECTIVE PAGES
Title
Effectivity
Effective Pages
Contents
Section 01
Section 02
Section 03
Page
Date
1 Aug 06/2015
2 Aug 06/2015
1 Dec 22/2009
2 Nov 30/2011
1 Nov 30/2011
2 Nov 30/2011
3 Nov 30/2011
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
Nov 07/2008
Nov 07/2008
Aug 02/2005
Apr 26/2005
Nov 07/2008
Nov 07/2008
Aug 06/2015
Aug 06/2015
Aug 06/2015
Aug 06/2015
Apr 26/2005
Nov 30/2011
Aug 06/2015
Nov 30/2011
Apr 26/2005
Nov 30/2011
Nov 30/2011
Mar 28/2006
Apr 26/2005
Aug 02/2005
Apr 26/2005
Apr 26/2005
Apr 26/2005
1
2
3
4
5
6
7
8
9
10
11
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Aug 02/2005
Aug 02/2005
Aug 02/2005
Aug 02/2005
Aug 02/2005
Aug 02/2005
Nov 30/2011
Title
20150806
Effectivity
Page
Date
Section 03
12 Nov 30/2011
Section 04
1
2
3
4
5
6
7
8
9
10
11
12
13
14
Aug 02/2005
Apr 26/2005
Dec 22/2009
Apr 26/2005
Aug 02/2005
Apr 26/2005
Apr 26/2005
Apr 26/2005
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
Nov 22/2012
Mar 28/2006
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
20111130
20150806
20091222
20111130
20111130
20111130
20111130
20081107
20081107
20050802
20050426
20081107
20081107
20050802
20050426
20091222
20050426
20050802
20050426
20050426
20050426
20111130
20111130
20111130
20111130
20111130
20111130
20150806
20150806
20150806
20150806
20050426
20111130
20150806
20111130
20050426
20111130
20111130
20060328
20050426
20050802
20050426
20050426
20050426
20111130
20111130
20111130
20111130
20050802
20050802
20050802
20050802
20050802
20050802
20111130
Section 05
20121122
20060328
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
20111130
EFFECTIVITY: ALL
EFFECTIVE PAGES
Page 1
Aug 06/2015
Title
Effectivity
Section 05
Section 06
Page
Date
29
30
31
32
Nov 30/2011
Nov 30/2011
Nov 30/2011
Nov 30/2011
1
2
3
4
5
6
7
8
9
10
11
12
13
Nov 30/2011
Aug 02/2005
Apr 26/2005
Nov 30/2011
Nov 30/2011
Apr 26/2005
Nov 30/2011
Apr 26/2005
Apr 26/2005
Apr 26/2005
Apr 26/2005
Nov 30/2011
Nov 30/2011
Title
Effectivity
Page
Date
20111130
20111130
20111130
20111130
20111130
20050802
20050426
20111130
20111130
20050426
20111130
20050426
20050426
20050426
20050426
20111130
20111130
EFFECTIVITY: ALL
EFFECTIVE PAGES
Page 2
Aug 06/2015
INTRODUCTION
1.
Scope of the Manual
A.
The Aircraft Recovery Manual, prepared by Bombardier Aerospace to help Airport
Authority, FBO, and/or aircraft recovery crews if an accident occurs with a Global Series
aircraft. Because there are many Completion Centers that do different passenger
compartment layout, it is not possible to give all different passenger compartment
layouts, in this manual.
B.
Global Series aircraft referred to in this manual, include:
C.
2.
Global Express
−
Global 5000
−
Gobal 5000 featuring Global Vision Flight Deck (GVFD)
−
Global Express XRS
−
Global 6000
No aircraft recovery operation will be the same as other recovery operations because:
−
The accident or the incident itself
−
The location of the aircraft
−
The amount of aid that is available locally
−
The weather conditions when the accident/incident occurred. Also, the effects of the
weather before and during the recovery operation
−
The number of persons that are available to help with the recovery.
Manual Organization
A.
3.
−
There are six sections in this manual:
−
Section 1 − INTRODUCTION
−
Section 2 − AIRCRAFT RECOVERY
−
Section 3 − AIRCRAFT − GENERAL
−
Section 4 − EMERGENCY INFORMATION
−
Section 5 − FIRE FIGHTING
−
Section 6 − GROUND SAFETY
Correspondence
Send your questions and suggestions to:
EFFECTIVITY: ALL
SECTION 01
Page 1
Nov 30/2011
By e−mail to: [email protected] (preferred) or
By phone at: Customer Response Centers (CRC)
Local and International: 514−855−2999
North America only: 1−866−JET−1247 (1−866−538−1247) Toll Free
Attention: Air Safety Investigation, Department 686−5
4.
Statement of Liability
A.
5.
This manual is intended to be used by Aircraft Crash Recovery crews involved in the
recovery of any Bombardier Global Series aircraft which becomes involved in an
accident or incident. It is also intended to help those persons planning for the unlikely
event that will require recovery actions. The actions described in this manual are
intended as recommendations only, as to how aircraft recovery tasks should be carried
out. Any omission of a task or an action, or any omission to a task or action, shall not be
interpreted as an admission of liability by Bombardier Inc., or any of its sub−groups of
affiliates or related entities.
Technical Glossary
Refer to Table 1. for a technical glossary of aircraft terminology and abbreviations.
Table 1 − TECHNICAL GLOSSARY
Abbreviation
Terminology
A/C
−
Aircraft
ac
−
Alternating Current
AFFF
−
Aqueous Fire Fighting Foam
APU
−
Auxiliary Power Unit
AUX
−
Auxiliary
CBR
−
California Bearing Ratio
dc
−
Direct Current
DISCH
−
Discharge
ELECT PWR
−
Electrical Power
ENG
−
Engine
EQP
−
Equipment Bay
FBO
−
Fixed Base Operator
EFFECTIVITY: ALL
SECTION 01
Page 2
Nov 30/2011
Table 1 − TECHNICAL GLOSSARY
Abbreviation
Terminology
FS
−
Fuselage Station
FT/SEC
−
Feet per Second
GVFD
−
Global Vision Flight Deck
IATP
−
International Air Technical Pool
ICAO
−
International Civil Aviation Organization
IIC
−
Investigator−in−Charge
LWR FUS
−
Lower Fuselage
MPH
−
Miles Per Hour
RAT
−
Ram Air Turbine
T/E
−
Trailing Edge
TYP
−
Typical
VFG
−
Variable Frequency Generator
6.
Dimensions
A.
Linear dimensions given in this manual are in inches. The metric equivalents are given in
parentheses ( ).
EFFECTIVITY: ALL
SECTION 01
Page 3
Nov 30/2011
TABLE OF CONTENTS
Section
Page
SECTION 01 − Introduction
Scope of the Manual
Manual Organization
Correspondence
Statement of Liability
Technical Glossary
Dimensions
1
2
3
SECTION 02 − Aircraft Recovery
Quick Reference Guide
Planning for Aircraft Recovery
General
Aircraft Recovery Plan.
Moving the Aircraft
General
Steps and Recommendations for an Efficient Aircraft Recovery
Terrain Consideration
General
Factors to Find the Most Practical Recovery Plan
Ground Conditions
1
2
3
5
20
SECTION 03 − Aircraft − General
Model Designation and Type
Aircraft Dimensions
Danger Areas
Doors
Composite Materials
Interior Configurations
1
2
SECTION 04 − Emergency Information
Emergency Access
Passenger Door
Overwing Emergency−Exit Door
Baggage Door
Aft Equipment−Compartment Door
Service Doors and Panels
Windshields and Windows
1
3
5
7
9
12
EFFECTIVITY: ALL
CONTENTS
Page 1
Dec 22/2009
Section
Page
SECTION 05 − Fire Fighting
General
On−Board Fire−Fighting Equipment
Engine/APU Fire Controls
Electrical Control Panels and Battery Locations
Flammable Fluids and Gases
Fuel System General Layout
Emergency Break−In Zone
Tires
Composite Material Fire Precautions
General
Dangerous Effects of Free Fibers
Control of Free Fibers
1
3
6
9
14
18
24
28
29
SECTION 06 − Ground Safety
Towing the Aircraft
General
Towing Aircraft with Bridle
Ground Lockpin
Safety Precautions
1
7
EFFECTIVITY: ALL
CONTENTS
Page 2
Nov 30/2011
AIRCRAFT RECOVERY
1.
Quick Reference Guide
A.
The leader of the recovery operation can use the Quick Reference Guide that follows as
a checklist for the recovery team to refer to.
(1) Do the weight and balance.
(a) Find the weight and balance of the aircraft to make an estimate of the limits to
jack and tow it.
(b) Record the quantity and location of cargo and fuel to calculate the weight and
balance.
NOTE:
You may have to calculate the weight and balance more than one
time during the recovery operations.
(2) Get initial data about the incident.
(a) Set up interface with the Investigator−in−Charge (IIC), local authorities, the
aircraft manufacturer’s (Bombardier) representative, and the owner’s agent or
representative.
(b) Tell the recovery crew surveyor to make a full estimate of the site as quickly as
possible. The type of accident site can have an effect on the aircraft removal.
(c)
Make a note of the slope of the terrain, the ground cover (e.g. trees, grass,
rock), and the distance from the runways, taxiways, and aprons.
(d) Make an analysis of the ground condition to calculate the bearing area
necessary to lift and move the aircraft.
(e) Choose suitable personnel (as well as the recovery crew members) and make
an estimate of the necessary equipment, and related manuals.
(f)
Get accommodations, transportation, work visas (when necessary), and
money for the recovery team.
NOTE:
The IIC must be at the site before this occurs.
(g) At the site, speak to local airport authorities, regulatory authorities, and
national investigating authorities.
Get data on the items that follow:
−
Local environment
−
Climate
−
Terrain structure
EFFECTIVITY: ALL
SECTION 02
Page 1
Nov 07/2008
−
Communications.
−
Local regulations for the defueling of the aircraft.
(3) Set Up Interfaces
(a) Make a detailed aircraft recovery plan (use a general recovery plan).
(b) Get permission from local and national authorities to continue with the
recovery operation. It is necessary for the different authorities to find the
cause(s) of an aircraft accident. You must know and follow the regulatory
authorities’ regulations, and the laws of the country in which the accident
occurs.
(c)
Move personnel and equipment to the recovery site.
(d) Prepare hangar and/or parking space for the aircraft. Refer to ARM section 3
para 6 for aircraft dimensions.
(e) Make sure that cranes are locally available. Also, make sure that other heavy
equipment, building materials and access roads are available. Some operators
are member of an organization that share their technical facilities, services and
recovery equipment (recovery kits). The International Air Technical Pool (IATP)
is the organization that manages the recovery pool arrangement.
(f)
If components are removed from the aircraft for recovery purpose, the center
of gravity weight and ballance location must be re−calculated befor the aircraft
is moved.
(g) If possible, remove all health risk payload (fuel, oils, dangerous materials,
catering, oxygen, squibs, galley and lavatory disposal and water) from the
aircraft.
NOTE:
Follow the applicable local regulations concerning defueling.
(h) If possible, remove the baggage, cargo and flyaway kit.
2.
(i)
If required, remove primary components as necessary.
(j)
Refer to ARM Section 6 − GROUND SAFETY for data on the installation of the
ground lockpins. These lockpins are used, where possible, to safety the RAT
and the landing gear for operations on the ground.
(k)
Prepare to tether, lift, and move the aircraft.
(l)
Complete the aircraft damage report when the aircraft recovery is completed.
The damage report is made by the Bombardier investigating team, or a
Technical Support/Engineering team that is specially assembled for the task.
Planning for Aircraft Recovery
EFFECTIVITY: ALL
SECTION 02
Page 2
Nov 07/2008
A.
General
CAUTION:
THE SPECIAL PROBLEMS THAT ARE RELATED TO AN AIRCRAFT
RECOVERY OPERATION MAKE IT NECESSARY FOR ONE APPROVED
PERSON TO DIRECT ALL OF THE OPERATION.
(1) Refer to the International Civil Aviation Organization (ICAO) document No.
9137−AN/898, Airport Services Manual; Part 5, "Removal Of Disabled Aircraft" as
an aid for aircraft recovery.
(2) The document gives the procedures to use for the recovery and/or removal of a
disabled aircraft. Some advanced procedures that are necessary are as follows:
(a) When you have to move an aircraft that cannot taxi or be towed with an
approved towbar or towing bridle, use other recovery procedures. The aircraft
may be lifted with pneumatic bags or cranes and move on a trailer or dollies.
(b) Advance planning is important to make sure that the equipment and persons
with the skills to do a recovery operation are available when necessary.
(c)
Prepare a full "Aircraft Recovery Plan" which may be started as soon as an
accident occurs and at the request of the IIC.
(d) Make sure to have the necessary emergency procedures. Give to the
applicable personnel, the tasks they are responsible for.
(e) Tell all major users of the airport about the airport management’s policies that
apply to the removal of disabled aircraft. Include applicable parts of this
document in the airport procedure.
NOTE:
B.
We recommend that a copy of this document be in the airport’s
"Aircraft Recovery Plan”.
Aircraft Recovery Plan.
(1) The Aircraft Recovery Plan includes:
(a) Guidelines for the fast removal of a disabled aircraft from airport operational
areas as well as the time necessary to prevent secondary damage to the
aircraft.
(b) Detailed grid maps for use during aircraft recovery operations. The maps must
show the topography of the airport site, approaches and adjacent areas. They
must also show roads, ditches, gates, ground conditions and other factors that
could have an effect on the aircraft recovery operations.
(c)
Details about access roads to all parts of the airport that are near overhead
power lines or bridges, specially those roads necessary for heavy equipment
such as cranes.
(d) Bombardier’s data on the types of its aircraft (Challenger, DeHavilland, Learjet
and Global Series) that use the airport. For aircraft recovery, the important
EFFECTIVITY: ALL
SECTION 02
Page 3
Aug 02/2005
data is in the weight and balance, lifting and moving, and weight reduction
numbers.
(e) The type and location of heavy or special equipment and the time necessary
for the equipment to get to the airport. Equipment to defuel aircraft must be
available to move to all areas or locations. Because of the dimensions of the
Global Series aircraft, cranes and slings can be used to lift the aircraft.
Because of this, you can include the availability of cranes in the recovery plan.
NOTE:
If not available, try to get aircraft recovery kits from other airports as
quickly as possible.
The ICAO "Airport Services Manual," Part 5, gives a worldwide list of
aircraft recovery kits.
(f)
Sources of personnel with different skills, ranging from laborers to aircraft
mechanics.
(g) The requirement for food, clothes, and shelter for the recovery crew.
(h) Flexible procedures for communications, security and safety for the recovery
operations, that are correct for the site.
(i)
An active inventory of locally salvage equipment that is available to the airport.
The operator can get aircraft removal equipment and crews through contracts
with airport owners, military airfields or aeronautical industries near the airport.
(j)
Airport rules must make sure of the items that follow:
1
The airport owner’s right to close all or part of the airport as necessary.
2
The limits of liability and penalties for violations.
NOTE:
(k)
Agreements from the IIC or the senior official of the
investigation team, for the airport owner to move a disabled
aircraft.
Contracts/agreements between aircraft operators and fixed base operators
must give each of them the capacity to move the types of aircraft they use or
those on which they do servicing. The movement must include minimum risk of
damage to the aircraft and to the airport. The contracts/agreements can be
with a single operator, a cooperative procedure with the airport authorities or a
joint procedure by more than one operator at the applicable airport. We
recommend that operators put their removal equipment together because of:
1
The logistical and time saving advantages of recovery kits that they own
together.
2
The economic advantages to single operators (they can buy fewer kits).
3
The improvements that come with more equipment because a larger
number of operators are together.
EFFECTIVITY: ALL
SECTION 02
Page 4
Apr 26/2005
(l)
The contracts/agreements must record the fixed base operator’s procedures
and capacity to do non−routine aircraft repairs on runways.
(m) Procedures and agreements for airports used jointly by civil and military
aviation.
(n) Analysis of data on recovery equipment, it shows that the type of recovery
equipment used does not affect the actual removal time.
(o) In the procedures for recovery equipment, look carefully at the items that
follow:
1
The full system to lift and to move the aircraft.
2
The mixture of recovery system components and the support equipment
necessary to move dangerous materials. Also, other equipment such as
cranes, dollies, and flatbed trucks.
NOTE:
3
3.
To move the Global Series aircraft, we recommend a
tractor/trailer with a bed of equally low height. This will decrease
the height the recovery team must lift a damaged aircraft.
If winch equipped heavy equipment (bulldozer etc) are available (because
of the frequent use of this type of equipment).
Moving the Aircraft
A.
General
(1) The primary reason to move the aircraft is its recovery as quickly as possible
without further or secondary damage. An up−to−date recovery plan is the best
procedure to decrease recovery time. Procedures for the recovery, as well as a
group of trained personnel must be components of the procedure.
(2) A correct estimate of the damage to the aircraft is very important. This will help to
find, in the shortest time, the procedure to do the recovery operation.
B.
Steps and Recommendations for an Efficient Aircraft Recovery
(1) Before you start a recovery operation, make sure of the correct safety precautions:
(a) Remove the aircraft batteries as quickly as possible. If it is not possible to
remove the batteries, disconnect and insulate the battery connectors. Refer to
Figure 1 for batteries locations.
(b) Close oxygen bottle valve.
(c)
If necessary, defuel the damaged aircraft to increase the speed of the recovery
operation.
NOTE:
EFFECTIVITY: ALL
SECTION 02
Page 5
Nov 07/2008
(2) Examine how the accident occurred. This will help to make an estimate of the
damage that occurred to the aircraft.
(3) After a check of the obvious damage, examine the structural condition of the
aircraft.
(4) Look for possible damage to other areas of the aircraft. The following are
indications of damage:
(a) Bulges in the wing or fuselage skin panels, at structural joints, or heavy fittings,
are indications of internal damage.
(b) Rivets, bolts, or fasteners of all types that tilt, are cut or loose, are also
indications of damage.
(c)
Torn, cracked or buckled fairings and other non−structural parts are causes for
close inspection of the structure below them. Think that damage to the
structure below these parts is possible until a close inspection shows
differently.
NOTE:
A close inspection may not be possible if the aircraft is wheels−up.
(5) Make a list of missing or unserviceable items as you make an estimate of the
damage.
WARNING:
FIND OUT IF THE STRUCTURE OF A DAMAGED AIRCRAFT CAN
HOLD ITS WEIGHT BEFORE YOU LOWER IT ON THE LANDING GEAR
FROM TRESTLES OR JACKS. YOU CAN CAUSE INJURY TO
PERSONS OR MORE DAMAGE TO THE STRUCTURE.
(6) Do an inspection of the aircraft structure before it comes off the trestles or jacks to
see if it is sufficiently strong to tow the aircraft on its landing gear. Lower the landing
gear only if:
(a) The IIC agrees.
(b) It is safe.
(c)
No more damage will occur.
CAUTION:
DO NOT REMOVE FUEL, CARGO, OR THE ENGINES IF THEY
KEEP THE AIRCRAFT'S CENTER OF GRAVITY. THIS WILL
PREVENT AN OVERLOAD AT THE JACKING POINT.
(7) The maximum weight of the aircraft on jacks are as follows:
NOTE:
These weights are for a undamaged aircraft. The damage caused by an
accident may cause lower maximum permitted loads at the jacking points.
Refer to Figure 2 for jacking point locations. It can be better to put the
aircraft on trestles (assembled on−site) if there is structural damage.
(a) The maximum permitted weight of the aircraft on jacks is 70 000 lb
EFFECTIVITY: ALL
SECTION 02
Page 6
Nov 07/2008
(31 751.5 kg).
(b) The maximum vertical jack loads for each location are as locations:
−
7 400 lb (3 356.58 kg) on the forward (nose) jacking point.
−
33 100 lb (15 013.9 kg) on each wing jacking point.
(8) If required remove the baggage and cargo from the aircraft. The baggage
compartment door opens in and up.
On Global Express, Global Express XRS and Global 6000 A/C
(9) Examine the damage to the fuel system to find the best procedure to defuel the
aircraft. The single−point refuel/defuel adaptor, fuel lines and tanks can have
damage. Refer to Figure 3.
On Global 5000 and Global 5000 Featuring GVFD A/C
(10) Examine the damage to the fuel system to find the best procedure to defuel the
aircraft. The single−point refuel/defuel adaptor, fuel lines and tanks can have
damage. Refer to Figure 4.
(11) Alternative procedures to defuel the aircraft are as follows:
NOTE:
(a) Suction defueling procedure.
1. The suction will break when one of the inlet points becomes open. This
procedure is slow and can mean that the fuel tank is not fully drained.
(b) Gravity defueling procedure.
WARNING:
MAKE SURE THAT THE FUEL LEVEL IN THE TANK IS BELOW
THE OPENING OF THE GRAVITY FUELING ADAPTER. IF IT IS
NOT, FUEL WILL SPILL OUT OF THE TANK. THIS CAN CAUSE
INJURY TO PERSONS.
1. Fuel will come out from the tank(s) if the level in the tank is higher than the
gravity fuel adaptor. To prevent this, make sure the fuel level in the tank is
below the gravity fueling adaptor opening.
2. If available, use a gravity defueling adaptor to drain fuel from the
underwing fuel drains into approved containers. Defuel the aft fuel tank at
the same time as the main fuel tanks. Use the suction procedure at the
single point refuel/defuel position. Use a suction hose in the overwing and
center tank gravity fueling adapter to remove the fuel if it is not possible to
remove it through the pressure refuel/defuel adaptor.
3. The quantity of fuel in the tank and the attitude of the aircraft will control the
amount of fuel you can remove.
EFFECTIVITY: ALL
SECTION 02
Page 7
Aug 06/2015
WARNING:
BEFORE YOU REMOVE THE ENGINE, MAKE SURE THAT THE
AIRCRAFT IS STABLE. IF IT IS NOT STABLE, THE AIRCRAFT
CAN FALL AND CAUSE INJURY TO PERSONS AND DAMAGE TO
THE AIRCRAFT.
(12) If the engines have to be removed to keep the weight and balance, make sure the
aircraft is level before the release of the load on the yokes. The aircraft must also
be stable to prevent movement because of an imbalance when an engine is
removed.
On Global Express A/C
(13) In recovery operations, there are two basic situations that will occur:
−
You can tow the aircraft on its landing gear
−
You must lift the aircraft on to a transport.
(a) If the landing gear stays serviceable after the aircraft has run off the runway or
taxiway, it may be possible to tow it by the main landing gear. Refer to Figure
10.
(b) If the landing gear has flat tire(s), there are some tow limits. For towing
restriction with flat tire. Refer to Figure 5.
(c)
Make an estimate of the ground’s load−bearing capacity and the slope of the
terrain in the recovery area. Make the path to tow the aircraft as smooth as
possible if it does not have concrete or asphalt. For landing gear
measurements and tire pressures, Refer to Figure 6.
CAUTION:
INFLATE THE FORWARD AND AFT LIFTING BAGS
SUFFICIENTLY TO KEEP THE AIRCRAFT STABLE. PUT THE
BAGS IN AREAS OF SUFFICIENT STRENGTH TO PREVENT
MORE DAMAGE TO THE AIRCRAFT.
(d) If the landing gear is unserviceable, use pneumatic lifting bags or cranes and
slings to lift the aircraft. Then put it on dollies or on a flatbed trailer.
On Global Express XRS and Global 6000 A/C
−
−
10.
(b) If the landing gear has flat tire(s), there are some tow limits. For towing
restriction with flat tire Refer to Figure 5.
(c)
EFFECTIVITY: ALL
SECTION 02
Page 8
Aug 06/2015
measurements and tire pressures, Refer to Figure 6.
CAUTION:
−
−
10.
(b) If the landing gear has flat tire(s), there are some tow limits. Refer to Figure 5
for towing restriction with flat tire.
(c)
measurements and tire pressures Refer to Figure 7.
CAUTION:
(16) Lift an aircraft that is on its fuselage with lifting bags as follow:
(a) Put the pneumatic bags below each wing, the forward fuselage and the aft
fuselage.
(b) Refer to Figure 8 for the restriction on lifting with the pneumatic bags and their
recommended position.
(c)
Keep the aircraft stable with cables while you lift it, or while the aircraft is on
the pneumatic bags.
(d) Inflate the pneumatic bags sufficiently to allow the installation of trestles or
jacks at the nose, wings and the rear fuselage support.
EFFECTIVITY: ALL
SECTION 02
Page 9
Aug 06/2015
(e) Put the cables at the nose jack point and the rear mooring points.
(17) Use a nose jack and normal jacking procedures to lift a nose−down aircraft around
the MLG axis.
(18) When you use cranes and slings to lift the aircraft, you must make an estimate of
the damage to the structure. This will help to find how much damage has occurred
and the location of strong frames to transmit the sling loads. Because each aircraft
recovery operation is different, Bombardier cannot recommend special sling
locations. Generally, use the nose jacking point (FS278.00), the passenger door aft
frame and the forward engine mounts to lift the aircraft. These are the strongest
frames locations. Refer to Figure 9.
(19) Lift the aircraft only in periods of very light or no winds. Because of the large areas
of wing, empennage and fuselage, small gusts of wind can cause large pendulum
movements.
(20) Make the aircraft stable during the lift. To help control its movements during the lift,
attach ropes to available strong points, such as the landing gear. If the engines are
removed, attach ropes to the forward engine mounts. During the lift, first level the
aircraft then lift it sufficiently high to put it on jacks or a flatbed trailer.
(21) If the aircraft cannot move on its landing gear, move it on a flatbed trailer. Refer to
Figure 9.
(22) Cranes and slings can be faster and easier to use in the recovery of the Global
Series aircraft.
EFFECTIVITY: ALL
SECTION 02
Page 10
Aug 06/2015
BATTERY CHARGER
BATTERY
gar_044
Aircraft Batteries and Static Ground Connections
Figure 1
EFFECTIVITY: ALL
SECTION 02
Page 11
Apr 26/2005
GLOBAL EXPRESS
GLOBAL XRS
GLOBAL 6000
FS989.75
FS758.516
FS278.00
GLOBAL 5000
GLOBAL 5000 FEATURING GVFD
FS278.00 (+32.00)
FUSELAGE
SUPPORT
SHORING
BEAM
WS166.13
WS166.13
JACKING
POINT
TYPICAL JACK
NYLON
PLUG
JACK
PAD
GAR_054
REAR FUSELAGE
SUPPORT
Structural Jack Points and Adapters
Figure 2
EFFECTIVITY: ALL
SECTION 02
Page 12
Nov 30/2011
RIGHT MAIN TANK
AFT AUXILIARY TANK
OP
SE
CLO
EN
CENTER WING TANK
LEFT MAIN TANK
CENTER
TANK
DRAINS
LOW PRESSURE
FILLER CAP
MAIN
TANK
DRAINS
GAR_004
FORWARD
TANK
(OPTIONAL FOR GLOBAL
EXPRESS ONLY)
PRESSURE REFUEL/DEFUEL ADAPTOR
Global Express, Global XRS and Global 6000 − Aircraft Defueling
Figure 3
EFFECTIVITY: ALL
SECTION 02
Page 13
Aug 06/2015
RIGHT MAIN TANK
SE
CLO
OPEN
CENTER WING TANK
LEFT MAIN TANK
CENTER
TANK
DRAINS
LOW PRESSURE
FILLER CAP
FAR02_003
MAIN
TANK
DRAINS
Global 5000 and Global 5000 Featuring GVFD − Aircraft Defueling
Figure 4
EFFECTIVITY: ALL
SECTION 02
Page 14
Nov 30/2011
ITEM
MAIN GEAR
NO.
CONDITION
TIRE
FOOTPRINT
EXAMPLES
PERMITTED
TO TAXI?
PERMITTED
TO TOW?
YES
YES
DISTANCE
PERMITTED
TO TAXI
AND TOW
NOSE WHEEL
ANGLE OF TURN
REMARKS
ONLY ONE
1
FLAT TIRE
(ANY TIRE)
SEE NOTES
UNLIMITED
NORMAL
TBD
1, 2, 5
UNLIMITED
NORMAL
TBD
1, 3, 4, 5
TWO FLAT TIRES
2
(ONE ON EACH AXLE)
YES
YES
YES
TWO FLAT TIRES
3
(ON ONE AXLE)
BOTH MAIN
YES
GEAR ONLY
(BRIDLE)
MINIMUM TO
CLEAR RUN−
WAY
10 DEGREES
TBD
MAXIMUM
SEE NOTES
SEE NOTES
1, 3, 4, 5, 6
YES
4
THREE FLAT TIRES
(ANY COMBINATION)
YES
BOTH MAIN
MINIMUM TO
10 DEGREES
GEAR ONLY
(BRIDLE)
CLEAR RUN−
MAXIMUM
TBD
SEE NOTES
1, 3, 4, 5, 6
WAY
YES
5
FOUR FLAT TIRES
YES
BOTH MAIN
MINIMUM TO
10 DEGREES
GEAR ONLY
(BRIDLE)
CLEAR RUN−
TBD
MAXIMUM
SEE NOTES
1, 3, 4, 5, 6
WAY
NOSE GEAR CONDITION
6
ONE FLAT TIRE
YES
YES
YES
7
TWO FLAT TIRES
YES
BOTH MAIN
GEAR ONLY
(BRIDLE)
TBD
UNLIMITED
TBD
UNLIMITED
MINIMUM TO
10 DEGREES
CLEAR RUN−
TBD
MAXIMUM
SEE NOTES
1, 2,TBD
4
SEE NOTES
1, 2, 5, 6
WAY
CAUTION: To taxi or to tow with two flat tires on same gear can result in wheel damage
NOTES
1
Avoid sharp turns, abrupt starts and stops.
2
Maximum speed pemitted to taxi or to tow aircraft = 5 mph (8kmh).
3
Maximum to taxi or to tow speed = 2 mph (3kmh).
4
After you clear the runway, or if additional tire fails, the airplane should be stopped
and serviceable wheel/tire assembly(ies) installed to obtain item number 2 or 6.
5
After any tire failure or excessive heat condition the affected wheel assembly
must be inspected per applicable Goodyear Overhaul Manual prior to further use.
6
Under a multiple failed tire condition, the affected landing gear assemblies
and linkages must be inspected for possible structural damage.
gar_005.dg
Towing/Taxiing with Flat Tires
Figure 5
EFFECTIVITY: ALL
SECTION 02
Page 15
Apr 26/2005
13.14 IN
(33.38 cm)
42 FT 5 IN
(12.93 m)
13 FT 4 IN
(4.06 m)
21.6 IN
(54.9 cm)
UNLOADED
GLOBAL EXPRESS
98 250 lbs (44 605 kg)
NOSE TIRE PRESSURE
150 − 155 PSI UNLOADED (1034 − 1069 kPa)
156 − 161 PSI LOADED (1076 − 1110 kPa)
MAIN GEAR TIRE PRESSURE
165 − 170 PSI UNLOADED (1138 − 1172 kPa)
172 − 177 PSI LOADED (1186 − 1220 kPa)
GAR_006
MAXIMUM RAMP WEIGHT
Global Express, Global XRS and Global 6000 − Landing Gear Measurements
Figure 6
EFFECTIVITY: ALL
SECTION 02
Page 16
Nov 30/2011
13.14 IN
(33.38 cm)
39 FT 8 IN
(12.12 m)
13 FT 4 IN
(4.06 m)
21.6 IN
(54.9 cm)
UNLOADED
GLOBAL 5000
87 950 lbs (39 894 kg)
NOSE TIRE PRESSURE
150 − 155 PSI UNLOADED (1034 − 1069 kPa)
(1076 − 1110 kPa)
156 − 161 PSI LOADED
MAIN GEAR TIRE PRESSURE
165 − 170 PSI UNLOADED (1138 − 1172 kPa)
172 − 177 PSI LOADED (1186 − 1220 kPa)
FAR02_008
MAXIMUM RAMP WEIGHT
Global 5000 and Global 5000 Featuring GVFD − Landing Gear Measurements
Figure 7
EFFECTIVITY: ALL
SECTION 02
Page 17
Nov 30/2011
Forward Fuselage:
Center of lifting bag to be located at,
or aft of FS280.00 bulkhead.
Wing (each side) :
or inboard of WS410.00 frame.
Rear Fuselage:
or forward of FS945.00 frame.
AIR SUPPLY
Restriction on lifting with Pneumatic Bags
Fuselage: 10.0 psi (69.0 kPa)
Allowable Lifting Pressure
Wing: 14.5 psi (100.0 kPa)
Allowable Lifting Loads
Rear Fuselage: 18 800 lb (8 528 kg)
Wing (per side): 26 300 lb (11 929 kg)
GAR_007
Forward Fuselage: 11 300 lb (5 126 kg)
Lifting with Pneumatic Bags
Figure 8
EFFECTIVITY: ALL
SECTION 02
Page 18
Mar 28/2006
NOTE
12 inches (0.30 m) WIDE STRAP PREFERRED,
10 inches (0.25 m) WIDE STRAP MINIMUM,
CHECK SLING LOAD RATING AND
USE MULTIPLE SLINGS TO CARRY
LOAD SAFELY.
SLING
ASSEMBLY
12 IN. (0.30 M)
WIDE STRAP
SLING
ASSEMBLY
12 IN. (0.30 M)
WIDE STRAP
FS925.00
FS347.00
FS280.00
FORWARD ENGINE
MOUNT (FS925.00)
WING JACK
POINT BEAM
REAR FUSELAGE
SUPPORT
B
A
GAR_008f
Aircraft Recovery with Cranes and Slings
Figure 9
EFFECTIVITY: ALL
SECTION 02
Page 19
Apr 26/2005
4.
Terrain Consideration
A.
General
(1) Type of terrain, weather conditions and structural damage to the aircraft are factors
to find the bearing area necessary to lift and move the aircraft. Get an experienced
civil engineer or earthworks contractor to make an assessment of the terrain
surface conditions, bearing loads and areas.
B.
Factors to Find the Most Practical Recovery Plan
(1) Make an estimate of the general terrain to find the best routing to tow the aircraft.
Structural damage to the aircraft can occur if it moves over terrain that is not
smooth. If necessary, grade the proposed tow routing to give a smooth surface for
the aircraft and tow vehicle(s).
(2) Make an estimate of how hard and smooth the surface is. Also, the possible effect
of rainfall and drainage on the load−bearing capacity of the terrain. Find the safe
bearing load and surface area of the terrain. The ground must have the same
condition for a depth of 8 in (20.3 mm), because the force necessary to tow an
aircraft changes as a function of the strength of the terrain.
(3) The type of terrain shows the applicable procedure to lift the aircraft:
(a) Use of jacks. Refer to Figure 2.
(b) Pneumatic bags. Refer to Figure 8.
(c)
C.
Mobile cranes and slings. Refer to Figure 9.
Ground Conditions
(1) Ground conditions are one of the primary factors in aircraft recovery operations.
Ground conditions have an effect on decisions to tow the aircraft, put tethers in the
ground, or set shoring (cribbing). From the results of ground tests, the recovery
team makes decisions about reinforcement of the terrain and the shoring (cribbing)
base.
(2) The California Bearing Ratio (CBR) is known as the standard for different ground
conditions:
(a) For the ground conditions that are related to shoring the aircraft (Refer to
Table 1).
(b) For the related bearing strength of different ground conditions (Refer to
Table 2).
EFFECTIVITY: ALL
SECTION 02
Page 20
Aug 02/2005
(3) See Table 1 and Table 2.
Table 1 − Ground Conditions To Shore the Aircraft
Surface
Type
Shoring (Cribbing) Necessary For Loads
That Roll
Max Allowable
Contact Pressure
psi
kPa
Minimum Contact
Area Needed
Each
2000
lb/in²
Each
141.
61kg/
cm²
Shoring (Cribbing) Necessary For
Loads To Jack
Max Allowable
Contact Pressure
psi
kPa
Minimum
Contact Area
Needed
Each
2000
lb/in²
Each
141.
61kg/
cm²
Soft Wet Clay
or Wet
Organic
Terrain
18.0
124.0
111.0
7.8
8.0
55.0
2500.0
175. 77
Loose Sand
or Sandy
Terrain
65.0
448.0
31.0
2.18
35.0
241.0
571.0
4.15
Sand with
Clay
100.0
690.0
20.0
1.41
50.0
345.0
400.0
28.12
Well Graded
Sand and
Medium Clay
180.0
1241.0
11.0
0.77
85.0
586.0
235.0
16.52
Sandy
Gravel, Clay
−Gravel or
Dry Clay
300.0
2068.0
6.7
0.47
165.0
1138.0
121.0
8.51
Compacted
Sandy
Clay−Gravel
N/A
N/A
N/A
N/A
200.0
1379 .0
100.0
7.03
EFFECTIVITY: ALL
SECTION 02
Page 21
Apr 26/2005
Table 2 − California Bearing Ratio (CBR) Soil Bearing Strength
Surface Type
Safe Bearing Load
Approximate Bearing Area Necessary
10 000lb
psi
kPa
in²
5 000kg
ft²
m²
Slate or Rock
230.0
1586.0
44.0
0.31
0.062
Concrete
156.0
1076.0
64.0
0.54
0.091
Hard Pan and Small
Gravel or Sand
138.0
951.0
72.5
0.50
0.103
Small Gravel and Sand
100.0
689.0
100.0
0.69
0.142
Gravel, Course Sand
or Medium Clay
62.0
427.0
161.0
1.12
0.229
Loose Sand and
Gravel Mixture
42.0
290.0
238.0
1.65
0.34
Medium stiff Clay
35.0
241.0
286.0
1.98
0.407
Loose Sand
30.0
207.0
333.0
2.31
0.474
Soft Clay or Earth
15.5
107.0
645.0
4.48
0.917
EFFECTIVITY: ALL
SECTION 02
Page 22
Apr 26/2005
MAIN BEAM
LEATHER
BINDING
ANCHOR
SHACKLE
WIRE ROPE
ASSEMBLY
TOWING AIRCRAFT FORWARD
ANCHOR
SHACKLE
WARNING
BEFORE THE AIRCRAFT IS TOWED,
MAKE SURE THAT ALL THE BOLTS
AND PINS ARE ATTACHED SAFELY.
ALSO MAKE SURE THAT THERE
ARE NO KINKS IN THE WIRE ROPE
ASSEMBLIES. YOU CAN CAUSE
INJURIES TO PERSONS AND
DAMAGE TO EQUIPMENT.
LEATHER
BINDING
TRAILING
ARM LINK
TOWING AIRCRAFT REARWARD
GAR_038
CAUTION
MAKE SURE THAT THE WIRE ROPE
ASSEMBLIES DO NOT TOUCH THE
BRAKE LINES OR THE WIRING
HARNESSES. ALSO MAKE SURE THAT
ONLY THE LEATHER BINDINGS OF
THE WIRE ROPE ASSEMBLIES TOUCH
THE LANDING GEAR. YOU CAN CAUSE
DAMAGE TO THE BRAKE LINES, THE
WIRING HARNESSES, OR THE
LANDING GEAR.
WIRE ROPE
ASSEMBLY
Towing by Main Landing Gear (MLG)
Figure 10
EFFECTIVITY: ALL
SECTION 02
Page 23
Apr 26/2005
AIRCRAFT - GENERAL
1.
2.
Model Designation and Type
A.
The Global Series aircraft is made by Bombardier Aerospace. The aircraft is an
all−metal, pressurized low wing monoplane with a full cantilever, swept−back wing.
B.
The aircraft has two BMW/Rolls Royce BR700–710A2–20 engines.
Aircraft Dimensions
A.
For the basic dimensions, including ground clearances. Refer to Figure 1.
B.
C.
3.
Danger Areas
A.
Persons who do aircraft recovery operations must know of the danger areas around:
the engines Refer to Figure 3.
the APU Refer to Figure 4.
4.
Doors
A.
The aircraft has the doors that follow:
−
Passenger/crew entrance door
−
Baggage compartment door on the left side of the aircraft
−
Aft equipment compartment door at the bottom of the rear fuselage
−
Different small service and access doors
−
Overwing emergency exit door located on the right side of the passenger
compartment.
NOTE:
5.
The entrance stairs attach to the passenger/crew door.
Composite Materials
EFFECTIVITY: ALL
SECTION 03
Page 1
Nov 30/2011
A.
Composite materials such as: Kevlar, Graphite, Fiberglass and hybrids are used in many
components of the Global Express Aircraft. Refer to Figure 5 for the locations of the
composite materials.
B.
components of the Global Express XRS Aircraft. Refer to Figure 6 for the locations of the
composite materials.
C.
6.
components of the Global 5000 and Global 5000 featuring GVFD Aircraft. Refer to
Figure 7 for the locations of the composite materials.
Interior Configurations
A.
Internal configurations will change according to customer options installed at the
completion centers.
EFFECTIVITY: ALL
SECTION 03
Page 2
Nov 30/2011
1
23 FT 6 IN
(7.16 m)
13 FT 4 IN
(4.06 m)
10 FT 1 IN
(3.07 m)
6 FT
(1.83 m)
7 FT 4 IN
(2.24 m)
13 FT 4 IN
(4.06 m)
94 FT
(28.65 m)
8 FT 10 IN
(2.69 m)
21 FT 1 IN
(6.43 m)
31 FT 9 IN
(9.68 m)
42 FT 7 IN
(12.98 m)
1
2
PASSENGER COMPARTMENT
DIMENSIONS
Length
Width (floor line)
Width (centre line)
Height
Volume
Floor area
48 FT 4 IN
6 FT 11 IN
8 FT 2 IN
6 FT 3 IN
2 100 FT³
335 FT²
(14.73 m)
(2.11 m)
(2.49 m)
(1.91 m)
(59.47m³)
(31.10 m²)
NOTE
For A/C 9002 to 9126 pre
SB 700−23−001. Measurement
at manufacturer’s weight empty.
For A/C 9002 to 9126 post
SB 700−23−001 and A/C 9127
and subs. Measurement at
manufacturer’s weight empty.
25 FT 6 IN
(7.77 m) 2
4 FT 1 IN
(1.25 m)
24 FT 10 IN
(7.57 m) 1
3 FT
(0.91 m)
5 FT 10 IN
(1.78 m)
GAR_057
86 FT 5 IN
(26.34 m)
99 FT 5 IN
(30.30 m)
Global Express, Global XRS and Global 6000 − Aircraft Basic Dimensions & Ground Clearances
Figure 1
EFFECTIVITY: ALL
SECTION 03
Page 3
Nov 30/2011
1
10 FT 1 IN
(3.07 m)
23 FT 6 IN
6 FT
(7.16 m)
(1.83 m)
13 FT 4 IN
(4.06 m) 7 FT 4 IN
7 FT 4 IN
(2.24 m)
13 FT 4 IN
(4.06 m)
94 FT
(28.65 m)
8 FT 10 IN
(2.69 m)
21 FT 1 IN
(6.43 m)
31 FT 9 IN
(9.68 m)
42 FT 7 IN
(12.98 m)
NOTE
1
PASSENGER COMPARTMENT
DIMENSIONS
Length
Width (floor line)
Width (centre line)
Height
Volume
Floor area
45 FT 8 IN
6 FT 11 IN
8 FT 2 IN
6 FT 3 IN
1 984 FT³
316 FT²
(13.92 m)
(2.11 m)
(2.49 m)
(1.91 m)
(56.18 m³)
(29.36 m²)
Measurement at manufacturer’s
weight empty (MWE)
1
4 FT 1 IN
(1.25 m)
25 FT 6 IN
(7.77 m)
3 FT
(0.91 m)
5 FT 10 IN
(1.78 m)
FAR_030
83 FT 9 IN
(25.53 m)
96 FT 9 IN
(29.49 m)
Global 5000 and Global 5000 Featuring GVFD − Aircraft Basic Dimensions & Ground Clearances
Figure 2
EFFECTIVITY: ALL
SECTION 03
Page 4
Nov 30/2011
DISTANCE TO AIRPLANE CENTERLINE
(6.09)
(6.09)
(12.19)
(9.15)
(3.04)
(15.24)
(METERS)
FEET
50
40
30
20
10
(3.04)
0
10
20
(12.19)
(9.15)
(15.24)
30
40
50
RADIUS
3 FT 6 IN
(1.07 m)
GROUND IDLE
INLET KEEP OUT ZONE
AXIAL DISTANCE
JET EXHAUST KEEP OUT ZONES
SINGLE ENGINE OPERATION
GROUND IDLE THRUST
(METERS)
0
FEET
(15.24)
50
(30.48)
100
(45.73)
150
1 FT 6 IN
(0.46 m)
150mph
(241.40kph)
102mph
(164.15kph)
62mph
(100.00kph)
(60.96)
200
(76.22)
250
GAR_010
34mph
(54.72kph)
Danger Areas − Engine Intake and Exhaust
Figure 3 (Sheet 1 of 4)
EFFECTIVITY: ALL
SECTION 03
Page 5
Aug 02/2005
(6.09)
(12.19)
(9.15)
(3.04)
(15.24)
(METERS)
FEET
50
40
30
20
10
(6.09)
(3.04)
0
10
20
(12.19)
(9.15)
(15.24)
30
40
50
RADIUS
12 FT 6 IN
(3.81 m)
TAKE−OFF
INLET KEEP OUT ZONE
5FT (1.52m)
AXIAL DISTANCE
(METERS)
0
50
150mph
(241.40kph)
(30.48)
100
102mph
(164.15kph)
(45.73)
150
(60.96)
200
62mph
(100.00kph)
TO 275 FT (83.84 m)
(76.22)
250
34mph
(54.72kph)
TO 550 FT (167.64 m)
GAR_011
SINGLE ENGINE OPERATION
TAKE−OFF THRUST
(15.24)
FEET
EFFECTIVITY: ALL
SECTION 03
Page 6
Aug 02/2005
(METERS)
(6.09)
(12.19)
(9.15)
(3.04)
(15.24)
CL
30
0
FEET
50
40
20
10
(6.09)
(3.04)
10
20
(12.19)
(9.15)
(15.24)
30
40
50
GROUND IDLE
INLET KEEP OUT ZONE
AXIAL DISTANCE
(METERS)
0
FEET
150mph
(241.40kph)
(15.24)
50
TWO ENGINE OPERATION
GROUND IDLE THRUST
102mph
(164.15kph)
(30.48)
100
62mph
(100.00kph)
(45.73)
150
(60.96)
200
(76.22)
250
TO 275 FT (83.84m)
GAR_001
34mph
(54.72kph)
EFFECTIVITY: ALL
SECTION 03
Page 7
Aug 02/2005
(METERS)
(6.09)
(12.19)
(9.15)
(3.04)
(15.24)
CL
30
0
FEET
50
40
RADIUS
20
12 FT 6 IN
(3.81 m)
10
(6.09)
(3.04)
10
20
(12.19)
(9.15)
(15.24)
30
40
50
TAKE OFF INTAKE
KEEP OUT ZONE
AXIAL DISTANCE
(METERS)
TWO ENGINE OPERATION
TAKE−OFF THRUST
5 FT
(1.52m)
150mph
(241.40kph)
60 FT (18.29 m)
WIDE APPROX.
102mph
(164.15kph)
62mph
(100.00kph)
(15.24)
50
(30.48)
100
(45.73)
150
(60.96)
200
TO 375 FT (114.33m)
(76.22)
TO 750 FT (228.66m)
250
GAR_002
34mph
(54.72kph)
FEET
0
EFFECTIVITY: ALL
SECTION 03
Page 8
Aug 02/2005
CENTERLINE TO EXHAUST
PERPENDICULAR TO
AIRCRAFT SKIN
5°
50°
90° F
(32° C)
15 FEET
(4.6 M)
20°
360° F
(182° C)
GAR_060
LEGEND
APU EXHAUST
DANGER AREA
Danger Areas − APU Exhaust
Figure 4
EFFECTIVITY: ALL
SECTION 03
Page 9
Aug 02/2005
SECTION 03
GAR03_012
NOSE LANDING
GEAR DOORS
HYDRAULIC
BAY DOOR
RADOME
RAT
COMPARTMENT
DOOR
BIRD STRIKE
BARRIER
FLAP
FAIRINGS
FORWARD
EQUIPMENT
COMPARTMENT
DOORS
ENGINE
COWLS
STAIRS
CABIN
FLOOR
MULTI−FUNCTION
SPOILERS
WHEEL
BINS
WINGLETS
BELLY
FAIRINGS
FLAPS
AFT
FUEL
TANK
PANELS
MLG DOORS
(INNER)
FAIRING
DORSAL
FAIRING
VERTICAL
STABILIZER
LEADING EDGE
SIDE PANELS
VERTICAL
STABILIZER
FAIRINGS
FIBERGLASS
HYBRID (MAINLY GRAPHITE)
GRAPHITE
KEVLAR
LEGEND
AILERON
THRUST REVERSER
TARGET DOORS
OUTER SKIN
RUDDER
HORIZONTAL
STABILIZER
ELEVATORS
Global Express − Composite Materials
Figure 5
EFFECTIVITY: ALL
Page 10
Aug 02/2005
SECTION 03
SAR03_012
NOSE LANDING
GEAR DOORS
HYDRAULIC
BAY DOOR
RADOME
RAT
COMPARTMENT
DOOR
BIRD STRIKE
BARRIER
FLAP
FAIRINGS
FORWARD
EQUIPMENT
COMPARTMENT
DOORS
ENGINE
COWLS
STAIRS
CABIN
FLOOR
MULTI−FUNCTION
SPOILERS
WHEEL
BINS
WINGLETS
MLG DOORS
(INNER)
BELLY
FAIRINGS
FLAPS
AFT
FUEL
TANK
PANELS
FWD FUEL TANK
AND NEW FAIRING
FAIRING
DORSAL
FAIRING
VERTICAL
STABILIZER
LEADING EDGE
SIDE PANELS
VERTICAL
STABILIZER
FAIRINGS
(MAINLY GRAPHITE)
FIBERGLASS
HYBRID
GRAPHITE
KEVLAR
LEGEND
AILERON
THRUST REVERSER
TARGET DOORS
OUTER SKIN
RUDDER
HORIZONTAL
STABILIZER
ELEVATORS
Global Express XRS and Global 6000 − Composite Materials
Figure 6
EFFECTIVITY: ALL
Page 11
Nov 30/2011
SECTION 03
FAR03_007
NOSE LANDING
GEAR DOORS
HYDRAULIC
BAY DOOR
RADOME
RAT
COMPARTMENT
DOOR
BIRD STRIKE
BARRIER
FLAP
FAIRINGS
FORWARD
EQUIPMENT
COMPARTMENT
DOORS
STAIRS
WINGLETS
WHEEL
BINS
CABIN
FLOOR
MULTI−FUNCTION
SPOILERS
ENGINE
COWLS
BELLY
FAIRINGS
MLG DOORS
(INNER)
FAIRING
DORSAL
FAIRING
VERTICAL
STABILIZER
LEADING EDGE
SIDE PANELS
VERTICAL
STABILIZER
FAIRINGS
FLAPS
FIBERGLASS
GRAPHITE
KEVLAR
LEGEND
AILERON
THRUST REVERSER
TARGET DOORS
OUTER SKIN
RUDDER
HORIZONTAL
STABILIZER
ELEVATORS
Global 5000 and Global 5000 Featuring GVFD − Composite Materials
Figure 7
EFFECTIVITY: ALL
Page 12
Nov 30/2011
EMERGENCY INFORMATION
1.
Emergency Access
A.
Passenger Door
(1) The Passenger Entrance Door is on the left side of the aircraft just after the flight
compartment. The door serves as a Type I Emergency Exit. Refer to Figure 1.
(2) Dimensions:
−
Height 6 ft (1.83 m)
−
Width 3 ft (0.91 m)
−
Height to the sill (one step below the floor line) 5 ft 11 in (1.80 m).
(3) To Open the Passenger Door from The external side do the following:
WARNING:
FULLY RELEASE THE PRESSURE FROM THE AIRCRAFT BEFORE
YOU TRY TO OPEN THE DOORS. IF YOU DO NOT DO THIS, THE
PRESSURE CAN DECREASE SUDDENLY. THIS CAN CAUSE INJURY
TO PERSONS AND DAMAGE TO EQUIPMENT.
(a) Push the flap in to get your fingers around the handle.
(b) Pull the handle out and push it up.
(c)
Pull out the handle and the door will lower automatically.
EFFECTIVITY: ALL
SECTION 04
Page 1
Aug 02/2005
INTERNAL
HANDLE
WARNING
CABIN MAYBE
PRESSURIZED
GAR_014
EXTERNAL
HANDLE
Passenger/Crew Door − Operation
Figure 1
EFFECTIVITY: ALL
SECTION 04
Page 2
Apr 26/2005
B.
(1) The overwing emergency−exit door is on the right side of the passenger
compartment. The door serves as a Type III Emergency Exit. Refer to Figure 2.
(2) Dimensions:
−
Height 3 ft (0.91 m)
−
Width 1 ft 8 in (0.51 m)
(3) To open the overwing emergency−exit door from the external side do the following:
(a) Apply hand pressure on the outside push plate and push the overwing−exit
door into the aircraft.
(4) To open the overwing emergency−exit door with the inside do the following:
(a) Hold the overwing emergency−exit door at the lower hand grip and the upper
latch handle.
WARNING:
BE CAREFUL WHEN YOU OPEN THE OVERWING
EMERGENCY-EXIT DOOR. THE DOOR WEIGHS
APPROXIMATELY 47 POUNDS (21.32 KG) AND IF YOU DO NOT
HOLD IT, IT CAN FALL AND CAUSE INJURY TO PERSONS OR
(b) Pull the upper latch handle marked EXIT PULL.
(c)
Tilt the top of the overwing emergency−exit door inboard and lift the door out of
the bottom hooks and the pin fittings.
EFFECTIVITY: ALL
SECTION 04
Page 3
Dec 22/2009
PUSH IN FLAP
PUSH DOOR INWARD
QUICK−
RELEASE
LATCH
MECHANISM
HAND GRIP
gar_015.dg
HOOK FITTINGS
Figure 2
EFFECTIVITY: ALL
SECTION 04
Page 4
Apr 26/2005
C.
Baggage Door
(1) The baggage door is a plug−type access door on the left hand side of the aft
fuselage section, forward of the aft pressure bulkhead. Refer to Figure 3.
(2) Dimensions:
−
Height 2 ft 9 in (0.84 m)
−
Width 3 ft 7 in (1.09 m)
−
Height to sill floor line 6 ft 7 in (2.01 m)
(3) To open the Baggage Compartment Door with the external handle do as follows:
(a) Push the external handle trigger marked PUSH to let the handle move out.
(b) Turn the external handle counterclockwise to the UNLOCKED position.
(c)
Push the door in and up on its tracks until the rollers touch the track stops and
the opening is clear.
(4) To open the Baggage Compartment Door with the internal handle do as follows:
(a) Pull the knob and turn the handle counterclockwise to release the latch.
(b) Pull the door in and up on the tracks until the rollers contact the track stops
and the opening is clear.
EFFECTIVITY: ALL
SECTION 04
Page 5
Aug 02/2005
EXTERNAL
HANDLE
EXTERNAL
HANDLE
TRIGGER
INTERNAL
HANDLE
gar_016.dg
Baggage Door
Figure 3
EFFECTIVITY: ALL
SECTION 04
Page 6
Apr 26/2005
D.
(1) The Aft Equipment Compartment of the Global Series aircraft is a non−pressurized
area. Access to the Aft Equipment Compartment is through a door in the aft
fuselage fairing. The door has a hinge at the forward end. It opens down and
forward. Refer to Figure 4.
(2) To open the Aft Equipment−Compartment Door do as follows:
(a) Push the external handle trigger marked PUSH to let the door handle move
out.
(b) Hold the door, turn the handle counterclockwise through 90°, and open the
door.
EFFECTIVITY: ALL
SECTION 04
Page 7
Apr 26/2005
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
.
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
.
. .
. .
. .
.
. .
. .
. .
.
. .
. .
. .
. .
. .
. .
. .
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
..
.
.
.
.
.
.
. .
.
.
.
. .
. .
. .
. .
. .
. .
. .
. .
. .
. . .
. . .
. .
. . .
. .
. .
. . .
. .
. . .
. .
. . .
. .
. .
. . .
. .
. . .
. .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
.
.
.
.
. .
.
.
.
.
.
.
.
.
.
.
.
.
..
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
.
. .
.
.
.
.
.
.
.
.
.
.
.
.
gar_017
Figure 4
EFFECTIVITY: ALL
SECTION 04
Page 8
Apr 26/2005
E.
Service Doors and Panels
(1) The Service Doors and Panels give access to equipment and systems all through
the fuselage. The Service Doors and Panels are made from Alclad, Carbondek,
graphite, or Kevlar (aramide). Refer to Figure 5.
EFFECTIVITY: ALL
SECTION 04
Page 9
Nov 30/2011
SECTION 04
EXTERNAL
COMMUNICATION
DOOR
GAR_020
DOOR FOR THE FORWARD
OVERBOARD−SERVICING CONNECTION
NLG
HYDRAULIC
BAY DOOR
ACCESS PANEL FOR THE
FORWARD EQUIPMENT
OXYGEN−FILL AND
INDICATOR DOOR
FORWARD EQUIPMENT−
COMPARTMENT DOOR
AFT OVERBOARD−SERVICING CONNECTION
POTABLE WATER
SERVICING
AC GROUND POWER
CONNECTION DOOR
DOOR FOR THE REFUEL/DEFUEL
CONTROL PANEL AND ADAPTER
GROUND AIR
SERVICING
APU
ACCESS
DOORS
RAM−AIR
TURBINE
DOOR
EXTERNAL−DC
GROUND POWER
ACCESS
AFT EQUIPMENT−
COMPARTMENT DOOR
ACCESS PANEL FOR
HYDRAULIC SYSTEM NO.3
SERVICING
FORWARD EQUIPMENT
COMPARTMENT DOOR
Global Express, Global XRS and Global 6000 − Service Doors and Panels
Figure 5
EFFECTIVITY: ALL
Page 10
Nov 30/2011
SECTION 04
EXTERNAL
COMMUNICATION
DOOR
FAR04_007
DOOR FOR THE FORWARD
OVERBOARD−SERVICING CONNECTION
NLG
HYDRAULIC
BAY DOOR
FORWARD EQUIPMENT
OXYGEN−FILL AND
INDICATOR DOOR
COMPARTMENT DOOR
AFT OVERBOARD−SERVICING CONNECTION
POTABLE WATER
SERVICING
ACCESS PANEL FOR
HYDRAULIC SYSTEM NO.3
SERVICING
FORWARD EQUIPMENT
GROUND AIR
SERVICING
APU
ACCESS
DOORS
RAM−AIR
TURBINE
DOOR
EXTERNAL−DC
GROUND POWER
ACCESS
AFT EQUIPMENT−
COMPARTMENT DOOR
AC GROUND POWER
CONNECTION DOOR
DOOR FOR THE REFUEL/DEFUEL
CONTROL PANEL AND ADAPTER
COMPARTMENT DOOR
Global 5000 and Global 5000 Featuring GVFD − Service Doors and Panels
Figure 6
EFFECTIVITY: ALL
Page 11
Nov 30/2011
F.
Windshields and Windows
(1) The flight compartment has two windshields and two side windows. The passenger
compartment has fourteen windows maximum on each side for the Global Express.
On the right side of the fuselage, one of the windows is in the Overwing
Emergency−Exit Door. All of the other passenger windows attach permanently to
their surround structure. Refer to Figure 7.
The windshields are made with layers of acrylic, polyvinyl butyl (PVB) and glass.
The side windows are made with layers of acrylic and PVB.
WARNING:
DO NOT TRY TO CHOP THROUGH THE WINDOWS. GO THROUGH
THE EMERGENCY BREAK-IN ZONE. IF YOU DO NOT DO THIS, YOU
CAN CAUSE INJURY TO PERSONS.
compartment has fourteen windows maximum on each side for the Global Express.
On the right side of the fuselage, one of the windows is in the Overwing
WARNING:
compartment has twelve windows maximum on each side for the Global 5000. On
the right side of the fuselage, one of the windows is in the Overwing
WARNING:
EFFECTIVITY: ALL
SECTION 04
Page 12
Nov 30/2011
SIDE WINDOW
WINDSHIELD
PASSENGER
COMPARTMENT
WINDOWS
SIDE WINDOW
PASSENGER
COMPARTMENT
WINDOWS
WINDSHIELD
WINDOW IN
OVER−WING
EMERGENCY
EXIT DOOR
PASSENGER
COMPARTMENT
WINDOWS
GAR_050
Global Express, Global XRS and Global 6000 − Windshield and Windows
Figure 7
EFFECTIVITY: ALL
SECTION 04
Page 13
Nov 30/2011
SIDE WINDOW
WINDSHIELD
PASSENGER
COMPARTMENT
WINDOWS
PASSENGER
COMPARTMENT
WINDOWS
PASSENGER
COMPARTMENT
WINDOWS
SIDE WINDOW
FAR04_001
WINDOW IN
OVER−WING
EMERGENCY
EXIT DOOR
WINDSHIELD
Global 5000 and Global 5000 Featuring GVFD − Windshield and Windows
Figure 8
EFFECTIVITY: ALL
SECTION 04
Page 14
Nov 30/2011
FIRE FIGHTING
1.
General
WARNING:
BE VERY CAREFUL NEAR THE FOUR OXYGEN BOTTLES BELOW THE
FLIGHT COMPARTMENT. EACH OXYGEN BOTTLE HAS A CAPACITY OF 50
FT³ (1.416M³). IF THESE BOTTLES ARE DAMAGED AND RELEASE THE
OXYGEN, THERE IS A POSSIBILITY OF AN EXPLOSION. THIS CAN CAUSE
INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
WARNING:
MAKE SURE TO DISCONNECT THE ELECTRICAL POWER TO THE APU AND
TO THE ENGINE FIRE EXTINGUISHER BOTTLES. THE EXTINGUISHER
BOTTLES HAVE PYROTECHNIC SQUIBS. IF YOU DO NOT DISCONNECT THE
ELECTRICAL POWER, THERE CAN BE AN EXPLOSION. THIS CAN CAUSE
INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
A.
The sentences below give the classes used for fire fighting.
−
For brake and wheel fires use only dry powder or class D fire extinguishers.
−
For all other parts of the aircraft use class B or C fire extinguishers.
Aerodrome Category for Rescue and Fire Fighting
B.
Category
Regulation
International Civil Aviation
Organization (ICAO)
6
ICAO Annex 14 −
Aerodromes
Federal Aviation
Administration (FAA)
B
FAR 139.315
Transport Canada (TC)
6
CAR 303 Subpart 3
Refer to Figure 1 for typical fire−fighting with small equipment .
EFFECTIVITY: ALL
SECTION 05
Page 1
Nov 22/2012
TOGGLE
PIN LATCHES
COWL
LATCHES
1. Press trigger plates
on toggle pin latches.
2. Hold left APU access door
and use a screwdriver to
open the 3 cowl latches
to release the doors.
3. Insert fire extinguishing
nozzle into APU enclosure.
LEFT APU ACCESS DOOR
INTERNAL ENGINE FIRE
APU ENCLOSURE FIRE
EXHAUST NOZZLE FIRE
BRAKE FIRE
GAR_046
AFT EQUIPMENT COMPARTMENT FIRE
Fire Fighting
Figure 1
EFFECTIVITY: ALL
SECTION 05
Page 2
Mar 28/2006
2.
On−Board Fire−Fighting Equipment
A.
The extinguishing system supplies fire extinguishant to the engine and auxiliary power
unit (APU) through a distribution system controlled in the flight compartment. The
extinguishing system also has a portable fire extinguisher for manual operation in the
aircraft. Refer to Figure 2 and Figure 3.
B.
The Global Series aircraft has two identical, crew−operated in−flight fire−fighting
systems. Each system has a spherical fire bottle of Halon 1301 located in the aircraft aft
section. The bottles are pressurized with dry nitrogen at a pressure of 625 psi (4 309.37
kPa) to push the Halon. Also three pyrotechnic squibs to discharge and direct the Halon.
One or both systems can be directed at No 1, No 2 engine or the APU. The control and
monitor panels are in the flight compartment.
C.
There is a portable fire extinguisher on the flight compartment bulkhead behind the
co−pilot’s seat. The fire extinguisher contains two pounds of Halon 1211 under pressure
of 100 psi (689.48 kPa).
EFFECTIVITY: ALL
SECTION 05
Page 3
Nov 30/2011
PORTABLE FIRE
EXTINGUISHER
NO.1 FIRE
EXTINGISHING
BOTTLE
GAR_045
NO.2 FIRE
EXTINGISHING
BOTTLE
Global Express, Global XRS and Global 5000 − On−Board Fire−Fighting Equipment
Figure 2
EFFECTIVITY: ALL
SECTION 05
Page 4
Nov 30/2011
PORTABLE FIRE
EXTINGUISHER
No 1 FIRE
EXTINGISHING
BOTTLE
JAR_001
No 2 FIRE
EXTINGISHING
BOTTLE
Global 6000 and Global 5000 Featuring GVFD − On−Board Fire−Fighting Equipment
Figure 3
EFFECTIVITY: ALL
SECTION 05
Page 5
Nov 30/2011
3.
A.
The control and monitor panels are in the flight compartment. Refer to Figure 4.
B.
To stop the engines do the following:
−
C.
Pull the LEFT/RIGHT DISCH PULL FIRE handle(s) in the flight compartment panel.
To stop the APU do the following:
−
Pull the APU DISCH PULL FIRE handle.
−
Then set the BATTERY MASTER SWITCH to OFF position.
EFFECTIVITY: ALL
SECTION 05
Page 6
Nov 30/2011
DISCH
2
1
A
P
U
PULL
DISCH
1
2
2
PULL
GAR_026
PULL
DISCH
1
Global Express, Global XRS and Global 5000 − Engine/APU Fire Controls
Figure 4
EFFECTIVITY: ALL
SECTION 05
Page 7
Nov 30/2011
JAR_002
Global 6000 and Global 5000 Featuring GVFD − Engine/APU Fire Controls
Figure 5
EFFECTIVITY: ALL
SECTION 05
Page 8
Nov 30/2011
4.
Electrical Control Panels and Battery Locations
A.
Refer to Figure 6 for aircraft and Avionics battery locations.
B.
To isolate electrical power do the following:
C.
D.
−
If engines are running select all the generators including APU generator control Push
Button Assembly switches to OFF.
−
Switch the BATTERY MASTER switch to OFF.
To disconnect main battery:
−
Open the aft compartment access door.
−
Turn the knob counterclockwise to disconnect the battery bayonet connector from
the battery.
To disconnect avionics battery:
−
Open the forward LH avionics equipment bay door.
−
Turn the knob counterclockwise to disconnect the battery bayonet connector from
the battery.
EFFECTIVITY: ALL
SECTION 05
Page 9
Nov 30/2011
ELECTRICAL
BATT MASTER
OFF
EXT AC
EXT DC
AVAIL
AVAIL
ON
ON
EMS
ON
GEN 1
GEN 2
GEN 3
GEN 4
FAIL
FAIL
FAIL
FAIL
OFF
OFF
OFF
OFF
PUSH OFF/RESET
APU GEN
RAT GEN
FAIL
ON
OFF
OFF
GAR_028
PUSH
OFF/RESET
Global Express, Global XRS and Global 5000 − Electrical Control Panels and Battery Locations
EFFECTIVITY: ALL
SECTION 05
Page 10
Nov 30/2011
BATTERY CHARGER
GAR_044
BATTERY
Global Express, Global XRS and Global 5000 − Electrical Control Panels and Battery Locations
EFFECTIVITY: ALL
SECTION 05
Page 11
Nov 30/2011
JAR_003
Global 6000 and Global 5000 Featuring GVFD − Electrical Control Panels and Battery Locations
EFFECTIVITY: ALL
SECTION 05
Page 12
Nov 30/2011
BATTERY
JAR_004
BATTERY CHARGER
Global 6000 and Global 5000 Featuring GVFD − Electrical Control Panels and Battery Locations
EFFECTIVITY: ALL
SECTION 05
Page 13
Nov 30/2011
5.
Flammable Fluids and Gases
Table 2 lists all flammable fluids and gases carried on the aircraft. The table also gives the
specifications and the commercial grades and capacities.
Table 2 − Flammable Fluids and Gases
CAPACITY
Cubic
Inches
U.S.
Gallons
Imperial
Gallons
Litres
Weight
Specification
or Commercial
Grades
Global
Express,
Global
Express
XRS and
Global
6000 Fuel
System
Total
Capacity
(Included
Forward
Fuel Tank)
—
6 523
5 432
24 689
44 572 lb,
(20 217 kg)
ASTM
D1655−Jet A
or Jet A1
MIL−T−83133A
JP−8
MIL−T−5624
JP−5
Global
5000 and
Global
5000
featuring
GVFD
Fuel
System
Total
Capacity
—
5 361
4 464
20 288
36 200 lb,
(16 420 kg)
Engine Oil
Tank
N/A
2 X 3.21
2 X 2.67
2 X 12.15
2 X 39 lbs
MIL−L−7808
Type 1 or
MIL−L−23699
Hydraulic
Reservoir
#1: 375
#2: 525
#3: 930
#1: 1.6
#2: 2.24
#3: 4.03
#1: 1.4
#2: 1.8
#3: 3.34
#1: 6.145
#2: 8.603
#3:
15.240
See Note 1
Skydrol LD−4
Chevron
HYJET lV
APU Oil
Tanks
N/A
5.18qt
4.30 qt
4.9 L
See Note 1
MIL−L−7808
Type 1 or
MIL−L−23699
EFFECTIVITY: ALL
SECTION 05
Page 14
Nov 30/2011
Table 2 − Flammable Fluids and Gases
CAPACITY
Cubic
Inches
U.S.
Gallons
Imperial
Gallons
Litres
Weight
Specification
or Commercial
Grades
Oxygen
Bottle
System
Pressure
1800 PSI
4 X 50.0
FT³
N/A
N/A
4X
1416.6
—
Therapeutic
Oxygen
Central Oil
Filling
Tank
N/A
1.5
1.25
5.7
See Note 1
MIL−L−7808
Type 1 or
MIL−L−23699
Note 1: Includes the weight of the Engine, APU oil and Hydraulic fluid.
A.
Refer to Figure 8 for locations of the reservoirs and tanks.
B.
C.
EFFECTIVITY: ALL
SECTION 05
Page 15
Nov 30/2011
SECTION 05
GAR_032
OXYGEN
BOTTLES (4X)
RIGHT
MAIN
TANK
FORWARD
TANK
(OPTIONAL)
CENTER
WING
TANK
AFT TANK
ENGINE
OIL TANK
HYDRAULIC
RESERVOIR
NUMBER 1
HYDRAULIC
RESERVOIR
NUMBER 2
LEFT
MAIN
TANK
HYDRAULIC
RESERVOIR
NUMBER 3
VFG OIL
TANK (2X)
ENGINE
OIL TANK
REPLENISHMENT
OIL TANK
VFG OIL
TANK (2X)
APU OIL TANK
Global Express, Global XRS and Global 6000 − Flammable Fluids and Gasses
Figure 8
EFFECTIVITY: ALL
Page 16
Nov 30/2011
SECTION 05
FAR05_010
OXYGEN
BOTTLES (4X)
RIGHT
MAIN
TANK
CENTER
WING
TANK
ENGINE
OIL TANK
HYDRAULIC
RESERVOIR
NUMBER 1
HYDRAULIC
RESERVOIR
NUMBER 2
LEFT
MAIN
TANK
HYDRAULIC
RESERVOIR
NUMBER 3
VFG OIL
TANK (2X)
ENGINE
OIL TANK
REPLENISHMENT
OIL TANK
VFG OIL
TANK (2X)
APU OIL TANK
Global 5000 and Global 5000 Featuring GVFD − Flammable Fluids and Gasses
Figure 9
EFFECTIVITY: ALL
Page 17
Nov 30/2011
6.
Fuel System General Layout
A.
The complete wing box is sealed to form three (Four Optional) fuel tanks, the left main,
the right main and center tank (and the forward tank which is optional). There is an aft
fuel tank which has two flexible elastomer bladders in a metal honeycomb structure
mounted in the aft section of the aircraft. Refer to Figure 10.
B.
The complete wing box is sealed to form three (Four Optional) fuel tanks, the left main,
the right main and center tank (and the forward tank which is optional). There is an aft
fuel tank which has two flexible elastomer bladders in a metal honeycomb structure
mounted in the aft section of the aircraft. Refer to Figure 10.
C.
The complete wing box is sealed to form three fuel tanks, the left main, the right main
and center tank. Refer to Figure 11.
D.
Baffles in the fuel tanks restrict unwanted fuel movement. In the main tanks, check
valves that swing let fuel flow only in the inboard direction. There are water drain valves
(self−closing, dual seal type), at all low points of the system.
E.
Refer to Figure 12 for the fuel controls in the flight compartment.
EFFECTIVITY: ALL
SECTION 05
Page 18
Nov 30/2011
RIGHT MAIN TANK
AFT AUXILIARY TANK
OPEN
C
LO
S
E
CENTER WING TANK
LEFT MAIN TANK
CENTER
TANK
DRAINS
LOW PRESSURE
FILLER CAP
MAIN
TANK
DRAINS
GAR_047
FORWARD
TANK
(OPTIONAL)
Global Express, Global XRS and Global 6000 − Fuel System Layout
Figure 10
EFFECTIVITY: ALL
SECTION 05
Page 19
Nov 30/2011
RIGHT MAIN TANK
OPEN
C
LO
S
E
CENTER WING TANK
LEFT MAIN TANK
CENTER
TANK
DRAINS
LOW PRESSURE
FILLER CAP
FAR05_006
MAIN
TANK
DRAINS
Global 5000 and Global 5000 Featuring GVFD − Fuel System Layout
Figure 11
EFFECTIVITY: ALL
SECTION 05
Page 20
Nov 30/2011
1.65
1.65
1.54
L
1.54
CRZ
EPR
SYNC
73.3
73.3
N1
789
789
ITT
L RECIRC
ON
N2
FF (PPH)
OIL TEMP
OIL PRESS
TOTAL FUEL (LBS)
14600
10000
2350
93 . 4
5750
115
81
− TRIMS −
NU
AIL
7.2
LWD
41550
14600
ND
STAB
RWD
NL RUDDER NR
GAR_034
ON
R RECIRC
93 . 4
5750
115
81
Global Express, Global XRS and Global 5000 − Fuel Controls in the Flight Compartment
Figure 12
EFFECTIVITY: ALL
SECTION 05
Page 21
Nov 30/2011
L
L RECIRC
INHIBIT
OFF
JAR_005
OFF
R RECIRC
INHIBIT
Global 6000 and Global 5000 Featuring GVFD − Fuel Controls in the Flight Compartment
EFFECTIVITY: ALL
SECTION 05
Page 22
Nov 30/2011
JAR_006
FUEL SYNOPTIC PAGE
Global 6000 and Global 5000 Featuring GVFD − Fuel Controls in the Flight Compartment
EFFECTIVITY: ALL
SECTION 05
Page 23
Nov 30/2011
7.
Emergency Break−In Zone
A.
Aircraft may or may not be painted with breakin marks. The area shown will offer the
least restriction to a forced entry into the aircraft. Refer to Figure 14.
B.
C.
EFFECTIVITY: ALL
SECTION 05
Page 24
Nov 30/2011
AIRCRAFT
CENTRE LINE
EMERGENCY
BREAK−IN ZONE
GAR_056
18 IN.
18 IN.
(45.72cm) (45.72cm)
Global Express − Emergency Break−In Zone
Figure 14
EFFECTIVITY: ALL
SECTION 05
Page 25
Nov 30/2011
AIRCRAFT
CENTRE LINE
EMERGENCY
BREAK−IN ZONE
FS477.00
18 IN.
(45.72cm)
18 IN.
(45.72cm)
SAR_004
FS509.00
Global Express XRS and Global 6000 − Emergency Break−In Zone
Figure 15
EFFECTIVITY: ALL
SECTION 05
Page 26
Nov 30/2011
AIRCRAFT
CENTRE LINE
EMERGENCY
BREAK−IN ZONE
FS477.00
FS509.00
18 IN.
(45.72cm)
FAR05_001
18 IN.
(45.72cm)
Global 5000 and Global 5000 Featuring GVFD − Emergency Break−In Zone
− Emergency Break−In Zone
Figure 16
EFFECTIVITY: ALL
SECTION 05
Page 27
Nov 30/2011
8.
Tires
A.
9.
If the wheels on the aircraft become hotter than usual (for example, because of hard
braking or under−inflation), there is a possibility that the fusible plugs can melt. This will
release tire pressure quickly. Thus, it is important for persons not to approach the wheels
from the sides. Refer to Figure 1.
Composite Material Fire Precautions
A.
General
(1) With the new generation aircraft, composite materials are widely used. These
materials are made by bonding layers of fiber together in a "criss−cross" pattern
with resins, epoxies and phenols.
(2) Refer to Figure 17 for the locations of the composite structures.
B.
Dangerous Effects of Free Fibers
(1) In the case of an aircraft fire, the bonding agents (resins, epoxies and phenols) can
become unstable and break down. This releases dangerous gases into the
atmosphere. Fire fighters and other personnel should avoid the downwind area of
the fire, specially when they do not use self−contained breathing equipment. As well
as dangerous gases, the fire also releases small particles of free fibers.
(2) When the fire is extinguished and the structure becomes cool, the bonding agents
stop the release of these free fibers. However, the hazards due to the release of
free fibers continues and can become a long term problem. This is because:
−
When The free fibers come in contact with fire, the fibers tend to break into
shorter lengths and smaller diameters. This makes them light and easily
airborne. The free fibers also absorb pyrolytic acid. This poisonous material is
picked up from the burned materials. The smoke from the fire can carry the free
fibers and can therefore send the contamination over a large area.
−
Without correct protection, personnel can breathe in the free fibers and they can
bond to a person’s respiratory system. They can also move to other internal
organs and cause damage. The free fibers are very stable and there is no
deterioration of the fibers in the body.
EFFECTIVITY: ALL
SECTION 05
Page 28
Nov 30/2011
C.
−
They will burn the eyes.
−
The ends of the fibers are very sharp. This will let them pass through clothing
and skin. If you rub the affected area, you can cause dermatitis which will
require medical treatment.
Control of Free Fibers
(1) As soon as the fire fighting and medical activities are completed, take steps to limit
the spread of the free fibers. This is important when you move the damaged
aircraft.
(2) Treat the components that can release free fibers as follows:
−
Keep the materials wet with Aqueous Fire Fighting Foam (AFFF) or water. With
the AFFF, wet the materials every six hours
NOTE:
−
Light oil, clear liquid furniture wax, polyacrylic acid or strippable paint, are
all good materials to contain free fibers. These liquids are not considered
to be a problem to future investigations.
Move the damaged aircraft the minimum distance possible and keep it on paved
surfaces when possible. This will make the removal of the contamination more
efficient.
(3) All personnel that work in the free fiber contaminated area must wear disposable
paper coveralls, heavy boots, thick leather gloves, goggles, and a dust mask. They
must discard the paper coveralls and dust mast when they leave the contaminated
area.
EFFECTIVITY: ALL
SECTION 05
Page 29
Nov 30/2011
SECTION 05
GAR05_012
NOSE LANDING
GEAR DOORS
HYDRAULIC
BAY DOOR
RADOME
RAT
COMPARTMENT
DOOR
BIRD STRIKE
BARRIER
FLAP
FAIRINGS
FORWARD
EQUIPMENT
COMPARTMENT
DOORS
ENGINE
COWLS
STAIRS
CABIN
FLOOR
MULTI−FUNCTION
SPOILERS
WHEEL
BINS
WINGLETS
BELLY
FAIRINGS
FLAPS
AFT
FUEL
TANK
PANELS
MLG DOORS
(INNER)
FAIRING
DORSAL
FAIRING
VERTICAL
STABILIZER
LEADING EDGE
SIDE PANELS
VERTICAL
STABILIZER
FAIRINGS
FIBERGLASS
GRAPHITE
KEVLAR
LEGEND
AILERON
THRUST REVERSER
TARGET DOORS
OUTER SKIN
RUDDER
HORIZONTAL
STABILIZER
ELEVATORS
Global Express − Composite Materials
Figure 17
EFFECTIVITY: ALL
Page 30
Nov 30/2011
SECTION 05
SAR03_012
NOSE LANDING
GEAR DOORS
HYDRAULIC
BAY DOOR
RADOME
RAT
COMPARTMENT
DOOR
BIRD STRIKE
BARRIER
FLAP
FAIRINGS
FORWARD
EQUIPMENT
COMPARTMENT
DOORS
ENGINE
COWLS
STAIRS
CABIN
FLOOR
MULTI−FUNCTION
SPOILERS
WHEEL
BINS
WINGLETS
MLG DOORS
(INNER)
BELLY
FAIRINGS
FLAPS
AFT
FUEL
TANK
PANELS
FWD FUEL TANK
AND NEW FAIRING
FAIRING
DORSAL
FAIRING
VERTICAL
STABILIZER
LEADING EDGE
SIDE PANELS
VERTICAL
STABILIZER
FAIRINGS
(MAINLY GRAPHITE)
FIBERGLASS
HYBRID
GRAPHITE
KEVLAR
LEGEND
AILERON
THRUST REVERSER
TARGET DOORS
OUTER SKIN
RUDDER
HORIZONTAL
STABILIZER
ELEVATORS
Global Express XRS and Global 6000 − Composite Materials
Figure 18
EFFECTIVITY: ALL
Page 31
Nov 30/2011
SECTION 05
FAR03_007
NOSE LANDING
GEAR DOORS
HYDRAULIC
BAY DOOR
RADOME
RAT
COMPARTMENT
DOOR
BIRD STRIKE
BARRIER
FLAP
FAIRINGS
FORWARD
EQUIPMENT
COMPARTMENT
DOORS
STAIRS
WINGLETS
WHEEL
BINS
CABIN
FLOOR
MULTI−FUNCTION
SPOILERS
ENGINE
COWLS
BELLY
FAIRINGS
MLG DOORS
(INNER)
FAIRING
DORSAL
FAIRING
VERTICAL
STABILIZER
LEADING EDGE
SIDE PANELS
VERTICAL
STABILIZER
FAIRINGS
FLAPS
FIBERGLASS
GRAPHITE
KEVLAR
LEGEND
AILERON
THRUST REVERSER
TARGET DOORS
OUTER SKIN
RUDDER
HORIZONTAL
STABILIZER
ELEVATORS
Global 5000 and Global 5000 Featuring GVFD − Composite Materials
Figure 19
EFFECTIVITY: ALL
Page 32
Nov 30/2011
GROUND SAFETY
1.
Towing the Aircraft
A.
General
(1) If the aircraft cannot be taxied, push or tow the aircraft to move it.
(2) To push or tow the aircraft, attach the towbar to the nose wheel axle with the lugs
on the towbar. Let the tow vehicle control movement of the aircraft. If the aircraft is
being pushed and you apply the aircraft brakes hard, this can cause the nose gear
to come off the ground.
(3) Refer to Figure 1 for the tow bar installation.
(4) Refer to Figure 2 for the turn radii.
(5) Refer to Figure 2 for the turn radii.
(6) Refer to Figure 3 for the turn radii .
B.
Towing Aircraft with Bridle
The following procedures is to tow the aircraft with Bridle.
Table 1 − Towing Equipment
REFERENCE
DESIGNATION
09X−10−04
TOWING BRIDLE
23X−51−01
HEADSET WITH MICROPHONE AND
LEAD
23X−51−02
HEADSET EXTENSION CORD
(1) Installation of Towing Bridle
EFFECTIVITY: ALL
SECTION 06
Page 1
Nov 30/2011
CAUTION:
DO NOT INSTALL THE WIRE ROPE ASSEMBLIES ON TOP OF THE
BRAKE LINES OR WIRING HARNESS. MAKE SURE THAT ONLY THE
LEATHER BINDING OF THE WIRE ROPE ASSEMBLIES TOUCHES
THE MAIN LANDING GEAR. YOU CAN CAUSE DAMAGE TO
EQUIPMENT.
(a) Attach the rope assemblies around each main landing gear as follows:
1
To tow the aircraft forward, release the clamps that hold the brake lines to
the main beam. Put the wire rope assemblies behind the brake lines on
the main beam, then around the main beam. Refer to Figure 4.
2
To tow the aircraft rearward, put the wire rope assemblies over the trailing
arm link and below the axle of each MLG. Refer to Figure 4.
NOTE:
WARNING:
3
Loosen or remove the retaining clips to put the wire rope
assembly between the MLG and the brake lines and the wire
harness.
MAKE SURE THAT THERE ARE NO KINKS IN THE WIRE
ROPE ASSEMBLIES. KINKS CAN CAUSE THE WIRE ROPE
ASSEMBLIES TO BREAK. THIS CAN CAUSE INJURY TO
PERSONS AND DAMAGE TO THE EQUIPMENT.
Tow the aircraft. Obey all the safety precautions (refer to Paragraph 1.D.).
(2) Removal of Towing Bridle
(a) Disconnect the wire rope assemblies from the anchor shackles.
(b) Remove the wire rope assemblies from the MLG.
(c)
Clean, lubricate, and put the towing bridle into storage.
EFFECTIVITY: ALL
SECTION 06
Page 2
Aug 02/2005
AXLE
ENGAGEMENT PIN
TOWBAR
TOP
TORQUE
LINK
SHEARPIN
LOWER
TORQUE
LINK
QUICK
RELEASE
PIN
AXLE
ENGAGEMENT PIN
GAR_036
TOWBAR
Equipment to Tow the Aircraft
Figure 1
EFFECTIVITY: ALL
SECTION 06
Page 3
Apr 26/2005
43 FT
(13.11 m)
128 FT 2 IN
(39.07 m)
56 FT 6 IN
(17.22 m)
7 FT 4 IN
(2.24 m)
20 FT 8 IN
(6.30 m)
14 FT
(4.27 m)
68 FT
(20.73 m)
45 FT 2 IN
(13.77 m)
53 FT 2 IN
(16.21 m)
MINIMUM
PAVEMENT
WIDTH
180 DEGREE
TURN
NOTE
GMF_009
MAXIMUM STEERING
Symmetrical and idle thrust
No differential braking
75 deg. steering angle
3 deg. slip
Dry runway
Slow continuous turn
Max A/C weight
AFT CG.
Global Express, Global XRS and Global 6000 − Turn Radii
Figure 2
− Turn Radii
EFFECTIVITY: ALL
SECTION 06
Page 4
Nov 30/2011
40 FT 4 IN
(12.30 m)
128 FT 2 IN
(39.07 m)
56 FT 6 IN
(17.24 m)
7 FT 4 IN
(2.3 m)
20 FT 8 IN
(4.23 m)
14 FT 0 IN
(4.26 m)
65 FT 4 IN
(19.92 m)
42 FT 6 IN
(12.95 m)
50 FT 6 IN
(15.39 m)
MINIMUM
PAVEMENT
WIDTH
180 DEGREE
TURN
NOTE
FAR06_003
MAXIMUM STEERING
1. Symmetrical and idle thrust
2. No differential braking
3. 75 deg. steering angle
4. 3 deg. slip
5. Dry runway
6. Slow continuous turn
7. Max A/C weight
8. AFT CG.
Global 5000 and Global 5000 Featuring GVFD − Turn Radii
Figure 3
EFFECTIVITY: ALL
SECTION 06
Page 5
Nov 30/2011
MAIN BEAM
LEATHER
BINDING
ANCHOR
SHACKLE
WIRE ROPE
ASSEMBLY
TOWING AIRCRAFT FORWARD
ANCHOR
SHACKLE
WARNING
BEFORE THE AIRCRAFT IS TOWED,
MAKE SURE THAT ALL THE BOLTS
AND PINS ARE ATTACHED SAFELY.
ALSO MAKE SURE THAT THERE
ARE NO KINKS IN THE WIRE ROPE
ASSEMBLIES. YOU CAN CAUSE
INJURIES TO PERSONS AND
LEATHER
BINDING
TRAILING
ARM LINK
TOWING AIRCRAFT REARWARD
GAR_038
CAUTION
MAKE SURE THAT THE WIRE ROPE
ASSEMBLIES DO NOT TOUCH THE
BRAKE LINES OR THE WIRING
HARNESSES. ALSO MAKE SURE THAT
ONLY THE LEATHER BINDINGS OF
THE WIRE ROPE ASSEMBLIES TOUCH
THE LANDING GEAR. YOU CAN CAUSE
DAMAGE TO THE BRAKE LINES, THE
WIRING HARNESSES, OR THE
LANDING GEAR.
WIRE ROPE
ASSEMBLY
Towing by Main Landing Gear (MLG)
Figure 4
EFFECTIVITY: ALL
SECTION 06
Page 6
Apr 26/2005
C.
Ground Lockpin
(1) Refer to Figure 5 , Figure 6 and Figure 7 for data on the ground lockpins that are
installed to safety the RAT and the landing gear for operations on the ground
D.
Safety Precautions
CAUTION:
WHEN YOU TOW THE AIRCRAFT WITH TORQUE LINKS DISCONNECTED,
OBEY THE PRECAUTIONS THAT FOLLOW:
-
DISCONNECT THE TOWBAR BEFORE YOU ARM THE NOSEWHEEL
STEERING.
-
DO NOT TOW AT MORE THAN 5 MPH (8 KM/H).
-
DO NOT PUSH REARWARD AT MORE THAN 3 MPH (5 KM/H).
-
DO NOT USE THE AIRCRAFT BRAKES TO STOP THE AIRCRAFT
UNLESS THERE IS AN EMERGENCY.
-
KEEP TURNS AS LARGE AS POSSIBLE.
-
MAKE ONLY SLOW CHANGES TO SPEED OR DIRECTION.
IF YOU DO NOT OBEY THESE PRECAUTIONS, DAMAGE TO THE
AIRCRAFT OR EQUIPMENT CAN OCCUR.
(1) Put the switch that controls the nose wheel doors to the SAFE position before you
put the ground lockpin into the RAT.
(2) Make sure that the switch to arm the nose wheel steering stays in the OFF position
while you tow or push the aircraft. Refer to Figure 8.
(3) Make sure to install ground lockpins in the NLG and the MLG. Refer to Figure 5 and
and Figure 6.
(4) Make sure to inflate the tires to their correct pressures if possible.
(5) Install the towing bridle (refer to paragraph 1.B.(1)).
(6) Remove all items from around the aircraft, such as ground equipment, that can
prevent the movement of the aircraft.
(7) Put a qualified technician in the flight compartment to monitor the brake system
pressure and operate the aircraft brakes.
(8) Put the Battery Master switch to ON position.
NOTE:
If the Battery Master switch is OFF, normal brakes operation will not
function. Only emergency brakes can be operated.
(9) Where conditions permit, start the APU to have electrical power on the aircraft.
EFFECTIVITY: ALL
SECTION 06
Page 7
Nov 30/2011
WARNING:
DURING THE OPERATION TO TOW THE AIRCRAFT, APPLY THE
BRAKES ONLY FOR AN EMERGENCY STOP. YOU CAN DRAIN THE
ACCUMULATOR PRESSURE WHICH CAN CAUSE THE BRAKES TO
NOT OPERATE. THIS CAN CAUSE INJURY TO PERSONS OR
(10) In the flight compartment, make sure that brake pressure is sufficient (1 100 psi
(7 584.28 kPa)). If the pressure is not sufficient, operate the electric motor−driven
pump for Number 3 hydraulic systems.
(11) Connect the intercom system between the driver of the tow vehicle and the
technician in the flight compartment.
(12) In an area that has little space, have a person at each wingtip to make sure of
sufficient clearance from objects and the aircraft.
(13) Before you move the aircraft rearward, have a person at the tail to make sure of
sufficient clearance from objects and the aircraft.
(14) Remove the chocks and release the parking brake.
(15) Tow the aircraft not more than 15 MPH (24 KM/H) or push the aircraft 3 MPH
(5 KM/H) maximum.
(16) After the tow operation, make sure the nose wheels are put to the center position.
Do the operations that follow:
(a) Apply the parking brake.
(b) Chock the wheels.
(c)
Release the parking brake.
(d) Disconnect the tow vehicle.
(e) Remove the tow bar or the towing bridle and park the aircraft.
NOTE:
In some cases, after a tow operation there is a difference between
the MLG strut heights. A qualified technician can make sure the
servicing of the struts is correct.
EFFECTIVITY: ALL
SECTION 06
Page 8
Apr 26/2005
GROUND
LOCKING
PIN
gar_039.dg
MLG Ground Lockpin
Figure 5
EFFECTIVITY: ALL
SECTION 06
Page 9
Apr 26/2005
GROUND
LOCKING
PIN
gar_040.dg
NLG Ground Lockpin
Figure 6
EFFECTIVITY: ALL
SECTION 06
Page 10
Apr 26/2005
GAR_058
GROUND SAFETY PIN
Ram−Air−Turbine (RAT) Ground−Lockpin
Figure 7
EFFECTIVITY: ALL
SECTION 06
Page 11
Apr 26/2005
NOSE STEER
LDG GEAR
ARMED
UP
OFF
HORN
MUTED
BTMS OVHT
WARN RESET
PILOT
EVENT
DN LCK
RELEASE
DN
gar_042.dg
Global Express, Global XRS and Global 6000 − Nose−Wheel Steering Switch
Figure 8
EFFECTIVITY: ALL
SECTION 06
Page 12
Nov 30/2011
GEAR AND BRAKES
NOSE
BTMS OVHT
WARNRESET
HORN
STEER
ARM
OFF
OFF
LDG GEAR
UP
DN LOCK
RELEASE
DN
AUTOBRAKE
OFF
LO
MED
JAR_007
HI
Global 6000 and Global 5000 Featuring GVFD − Nose−Wheel Steering Switch
Figure 9
EFFECTIVITY: ALL
SECTION 06
Page 13
Nov 30/2011

Ground Safety

Transcription

Similar documents

Wherever you are. Whenever you need it.

global xrs - Skyservice

RAF Brize Norton, Oxford

aircraft specifications airbus 320-232 4l-ajf

Airvan8 Brochure

Loftleidir-Icelandic

proudly offers FOR SALE 1976 Beechcraft Baron 58

Fat Albert - California Capital Airshow

brochure - Aliserio – Bizjet Maintenance

North Atlantic MNPS Airspace Map